Ultralight and Very Light Helicopter Rotor Data

• Autorzy: Dudnik Vitaly , Karabut Victor

Identyfikatory

DOI

10.2478/tar-2023-0008

• Języki publikacji: EN

Abstrakty

EN

In recent years, a significant number of one- and two-seat lightweight helicopters have come into existence, and this makes it possible to analyse parameters and determine dependencies for this class of helicopters. The knowledge of such dependencies is necessary at the preliminary design stage. The analysis performed in this paper and its comparison with the statistical data of all categories of helicopters made it possible to determine the necessary corrections in the methods of determining the parameters of the helicopter’s rotor systems.

Słowa kluczowe

EN

ultralight helicopter; main rotor; blade; preliminary design

• Wydawca: Wydawnictwa Naukowe Sieci Badawczej Łukasiewicz - Instytutu Lotnictwa
• Czasopismo: Transactions on Aerospace Research
• Rocznik: 2023
• Tom: Nr 2 (271)
• Strony: 17--24
• Opis fizyczny: Bibliogr. 9 poz., fot., rys., wykr., wzory

Twórcy

autor

Dudnik Vitaly

• Silesian University of Technology, Akademicka 2A, 44-100 Gliwice, Poland
• RS Helikopter GmbH, Brienner Str. 7 80333, München, Bayern, Germany

• https://orcid.org/0000-0002-5798-8019

autor

Karabut Victor

• RS Helikopter GmbH, Brienner Str. 7 80333, München, Bayern, Germany

• https://orcid.org/0000-0002-4310-4083

Bibliografia

• [1] Rand, O. and Khromov, V. Helicopter Sizing by Statistics. American Helicopter Society, 58th Annual Forum. Montreal, Canada (2002).
• [2] Raymer, D. Aircraft Design: A Conceptual Approach, 3rd ed. American Institute of Aeronautics and Astronautics, Inc., Reston, Virginia (1999).
• [3] Fradenburg, E. “The First 50 Years Were Fine But What Should we do for an Encore? Alexander A. Nicolsky Lecture.” Journal of American Helicopter Society (1994). p.3-20.
• [4] Krenik, A. and Weiand, P. Aspects on Conceptual and Preliminary Helicopter Design. Deutscher Luft- und Raumfahrtkongress, Document 420207 (2016).
• [5] Losev, L. Preliminary Determination of the Helicopter General Parameters Under Criteria of Take-off Mass Minimum. Kharkov Aviation Institute, Kharkov (1988).
• [6] Losev, L. and Ryabkov, V. Choice of The Coaxial Helicopter Parameters Under Criteria of Take-off Mass Minimum, Kharkov Aviation Institute, Kharkov (1999).
• [7] Tishchenko, M. Choice of The Helicopter Parameters At The Preliminary Stage of Design. Moscow Aviation Institute, Moscow (2010).
• [8] Johnson, W. Design and Analysis of Rotorcraft. NASA/tP-2015-218751, NACA, Ames Research Center, (2015).
• [9] Xin-Lai, L., Hu, L., Gang-Lin, W., and Zhe, W. “Helicopter Sizing Based on Genetic Algorithm Optimized Neural Network, Chinese.” Journal of Aeronautics Vol. 19 No. 3 (2006). p. 212-218.

Uwagi

Opracowanie rekordu ze środków MNiSW, umowa nr SONP/SP/546092/2022 w ramach programu "Społeczna odpowiedzialność nauki" - moduł: Popularyzacja nauki i promocja sportu (2024).